Airplane brake



Sept. 30, 1952 B. J. DROZINSKI AIRPLANE BRAKE 2 SHEETS-SHEET 1 Filed Aug. 17, 1948 INVENTOR. aeo/v/suw .1 aeaz/r/s/r/ BY v ay, &0/2/a i ATTOB/YEKS B. J. DROZINSKI AIRPLANE BRAKE Sept. 30, 1952 2 SHEETSSHEET 2 Filed Aug. 17, 1948 INVENTOR. 630M800? J. DKOZl/VSK/ Arrokm-vs Patented Sept. 30, 1952 "UNITED STATES" PA-TENT ,o FIcE'.

I 2,612,332 V W I 1 AIRPLANE BRAKE e v Bronislaw J. Drozinski, Cleveland, Ohio 7 Application August 17, Serial 24,639 f r I 1 The present invention relates to braking systems' for airplanes and more particularly to braking systems adapted to release parachute type air drags-at the Option of the aircraft pilot.

An object of the present invention is to provide braking systems for aircraft which will effectively reduce the speed of aircraft at the time of landing whereby high speed aircraft can safe-- ly he landed within relatively short spaces, such as on aircraft carriers.

Another object of the invention is to provide braking systems for aircraft which can be applied to existing aircraft without altering the structure thereof.

being. made to the accompanying drawings wherein:

Fig. 1 illustrates one form of braking system applied to the wing structure of an airplane;

Fig. 2 is a side view in elevation of a parachute type brake drag container;

Fig. 3 is a view in section taken on line 33 of Fi 2;

ig. 4 is a view in section taken on line 4-4 of Fig. 2;

I Fig. 4a is a view in section taken on line fla-da of Fig. 2; I

Fig. 5 is a fragmentary front view of an airplane having another form of braking system incorporated therein, the system being shown in operation;

Fig. 6 illustrates a side view of the second form of braking system as incorporated in the wing of an airplane;

Fig. 7 is a longitudinal sectional view of a parachute type brake drag container for installation within the confines of a wing; and,

Fig. 8 is a view in section taken on line 88 of Fig. '7.

bands are provided with suitable bases l4 for" 2 Claims. (Gifiin's) 26 and a yoke portion 21.

attachment to the wing structure- The end portions of the shell l2 are suitably attached to the bands l3, as by welding.

The opposite ends of the container II) are closed by dome shaped end caps l5 and IB, which. extend into the bands I3 and are secured theretoas by welding. Caps l5 and 16 provide a streamlining effect to minimize air drag of the container.

It will be noted .that the upper side. of the semi-cylindrical shell I2 is open intermediate the bands l3 and this opening is adapted to be closed by two cover members 20 and 2|, which members are in the form of segments of a cylinder so that whenthe covers are .closed they, together with shell l2, form a cylindrical enclosure. The members 20 and 2| are rigidly attached to rods 22 and 23 which are journalled at opposite ends in the bands I3 and the cover members are adapted to be swung about their lower edges by rotation of the rods. Thus, the cover members may be moved to open and close the top of the shell [2.

The rotation of the rods 22 and 23 is controlled by the pilot by a remote control system which includes an actuating member 25 having a stem The stem 26 projects downwardly through an opening in the forward end of the container l0 and beneath the surface of the wing for attachment to a suitable lever, notshown, which is operated by the pilot to raise or lower the member 25. One end of the yoke 21 is connected by a lever 28 to-the rod 22 and the opposite end of the yoke is connected to rod 23 by a lever 29. The levers 28 and 29 are keyed to' the respective rods 22 and 23 so that when levers 28 and 29 are rotated by vertical movement ofmember25 the covers 29 and 21 will be swung to their open or closed positions. The ends of the levers 28 and 29 connected to yoke 21 are slotted to accommodate foreshortening of the distances between the axes of the respective rods and the points of connection with the yoke as the member 25 is moved upwardly. The connections between th yoke 21 and levers 28 and 29 are effected by pins 31 which loosely project through the slots of the levers, openings in the yoke and through slots 32 formed in a plate 33 attached to the interior of the end cap l5 and extending transversely of the axis of the container Hi. It will be seen that the pins cooperate with the edges of the slots 32 to provide a vertical guide for the operating member 25.

A parachute is adapted to be carried within the container l0 and the shrouds 5| thereof are 'chuteiare'attached."

anchored to a ring 52 formed integral with the plate 33. The parachute 50 is folded in such a manner that when the covers 20 and 2| are Referring now to Figs. 5 through 8, I have shown a second form of the invention whereina parachute container 60 is mounted within the desirable to use the brakes the pilot releases lock I member 8! and applies pneumatic pressure for forcing the piston outwardly thereby ejecting the parachute from the container and applying an air drag for reducing the speed of the aircraft. The piston will come to rest against the inner ring 66.

Preferably, a container 60 is provided on each side of the fuselage of the aircraft, although it is to be understood thatv more or fewerfcould be mounted on any desirable part or parts of the airplane.

the container outwardly above the wingsurface.

The container 60 comprises a cylindrical mem ber 6| closed at oneend and having the plane 'of the opposite open end diagonal to the axis thereof, the angle of the plane of the end-being determined by the position'of the container in the wing and the contour of the upper surface of the wirig" whereby the plane of the opening will be substantially coincident with theplane 0f the wing'adj acent to the'endof thecontainer.

A cap 'n'iember '64 is secured over the closed end of member BI and the cap is provided with a ring. form'ationGS for anchoringthec'ont'ainer 60 The ring 67' is pneumatic pressure entering the member 6| through a port 16 which 'is adapted to be connectedby a suitable line, not'sh'o'wn, to an air pressure system in the plane and under the control of the 'pilot, th'e' air system and control not being shown since such may be of "conventional 'desig'n The p'isto'n 15 is provided with a ring formation 78 to which'theshrou'ds of the para- The open end'of member Blis adapted to be closed :by a cover pl'ate'fl'll which is hinged at the upper pointthereo'f'to the ringfi'l, and the lower 'edge'o'f 'the'cover' B0 is adapted to be locked in 'place'by ala'tch ni'ember'iil "which is mounted on "a rod' 82; which rod is slidable in abushing'83 supported-on" the lower side of the member 6|.

A 's'pring '84 is mounted'b'etween the lug (Band '2, head '85 on the end of rod 82 for urging the latch member '8l to the latching position; Rod

82 may 'be moved to the 'unlatched position by the pilot through'a linkage-system which includes link 86 connected to one end of rod 82 and to alever'81, which lever is adapted to be actuated by alink 88 suitably connected to a lever under the control of the pilot, but not shown.

"*Aparachute 90, such as that shown in Fig. 6,

'is adapted to be carried within member GI and resistance o-fiered by the system.- When it is The'container '60 is mounted within the wing The parachutes may be of any suitable size and yrthey-may include a small pilot parachute for 15 confines of the wing structure and mechanism is provided for projecting the parachute from assuring quick opening of the main parachute.

"It will'be understood that although I have 1; described but two forms of the invention, it is to be understood that other forms might be adopted, all falling within the scope of the claims which follow.

I claim: i t

, l.-:A parachute type brake mechanism for -an airplane wing structure comprising a cylindrical chamber disposed-within the wingand below the top surface thereof,- said chamber extending substantiallyparallel to the-line of flight and having the'rear endthereof open to the exterior of the wing; a hinged cover for the opening; remote control mechanism for releasably securing the cover in closed position; a piston in said chamber adapted to be moved in response to pneumatic pressure in'the forward-end of the chamber; a parachute adapted to be carried in said chamber and anchored to said piston; and means. for directingpneumatic pressure against the forward "end of the piston for positively ejecting the parachute from the chamber into the'airstreamabove the 'wing. L

2. :An airplane wing structure comprising a cylindrical chamber disposed within the wing'and below the top surface thereof, said 'chamber extending substantially parallel to the line of flight and having the rearend thereof open to the exteriorx'o'f-theWing;"a hinged cover for the opening, said cover'extending substantially flush with the upper surface of the wing adjacent'to said opening; remote control mechanism for 'releasably securing the cover'in closed position;

a piston insaid chamber adapted to be moved in response to pneumatic pressure in the forward end of the chamber; 'a'parachute'adapted to be carried in said chamber and anchored to said piston; and means for directing pneumatic pressure against the forward end of the piston for positively ejecting'the parachute from the chamber. BRONISLAW J. DROZINSKI.

- REFERENCES CITED 7 The following references are of record in the file of this patent:

UNITED STATES PATENTS 

